27th european space thermal analysis workshop · between the tmm results and the cfd results...

ESA-WPP-338February 2014

Proceedings of the

27th European

Space Thermal Analysis

Workshop

ESA/ESTEC, Noordwijk, The Netherlands

3–4 December 2013

credits: National Aerospace Laboratory NLR

European Space AgencyAgence spatiale européenne

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Abstract

This document contains the presentations of the 27th European Space Thermal Analysis Workshopheld at ESA/ESTEC, Noordwijk, The Netherlands on 3–4 December 2013. The final schedule forthe Workshop can be found after the table of contents. The list of participants appears as the finalappendix. The other appendices consist of copies of the viewgraphs used in each presentation andany related documents.Proceedings of previous workshops can be found at http://www.esa.int/TEC/Thermal_controlunder ‘Workshops’.

Copyright c© 2014 European Space Agency - ISSN 1022-6656

Please note that this document contains clickable hyperlinks which are shown as blue text.

27th European Space Thermal Analysis Workshop 3–4 December 2013

http://www.esa.int/TEC/Thermal_control

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Contents

Title page 1

Abstract 2

Contents 3

Programme 6


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Appendices

A Welcome and introduction 9

B Thermal Concept Design Tool — Flux calculation results and the new toolpresentation 17

C Evaluation of Heat Transfer Parameters from CFD for Use in TMM in Case ofGas Convection in Vented Cavities 33

D Introduction to Simulation Data Management 43

E EVATHERM for Early Validation of Thermal Control 59

F Thermo-electrical Detailed Analysis 73

G Correlating thermal balance test results with a thermal mathematical modelusing evolutionary algorithms 89

H Exchange of Thermal Models — Challenges and Solutions 109

I The KT Thermal Mapping Tool — an semi-automated temperature transferbetween structural and thermal models 119

J Mapping nodal properties between dissimilar nodal representations of S/Cstructures using ESATAN-TMS 137

K MASCOT — Thermal subsystem design 151

L LHP MODULE SOFTWARE — Application at System Level 165

M Time dependent behaviour of pumped two-phase cooling systems — Experi-ments and Simulations 177

N Study on the utilization of the FHTS extension of ESATAN-TMS for the thermalmodeling of a bi-propellant satellite propulsion system 193

O Thermal Modeling of CubeSats and Small Satellites 205

P E-THERM POLICY 221

Q ESATAN Thermal Modelling Suite — Product Developments and Demonstration 235

R SYSTEMA-THERMICA — Launcher Case Set-up and Thermal Analysis 261

S First Application of Esatan-TMS r6 Solids for a Launcher Upper StageThermal Model 279


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T Enhancement of ray tracing method for radiative heat transfer with new Isocellquasi-Monte Carlo technique and application to EUI space instrument baffle 291

U Calculation of Optimal Solar Array Steering Laws for Temperature Critical Missions303

V BepiColombo MTM STM Thermal Test 311

W List of Participants 321


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Programme Day 1

9:00 Registration

9:45 Welcome and introductionHarrie Rooijackers (ESA/ESTEC, The Netherlands)

10:00 Thermal Concept Design Tool — Flux calculation results and the new tool presentationAndrea Tosetto & Matteo Gorlani (Blue Engineering, Torino, Italy)

Harrie Rooijackers (ESA/ESTEC, The Netherlands)

10:25 Evaluation of Heat Transfer Parameters from CFD for Use in TMM in Case of GasConvection in Vented Cavities

Christian Wendt (Astrium Space Transportation, Bremen, Germany)

10:50 Introduction to Simulation Data ManagementPeter Bartholomew (MDAO Technologies, United Kingdom)

11:15 Coffee break in the Foyer

11:45 EVATHERM for Early Validation of Thermal ControlFabrice Mena (Astrium SAS, France)

12:10 Thermo-electrical Detailed AnalysisFrançois Mercier & B. Samaniego & V. Gineste & L. Gajewski & A. du Jeu (Astrium SAS, Toulouse, France)

12:35 Correlating thermal balance test results with a thermal mathematical model usingevolutionary algorithms

Niek van Zijl & B. Zandbergen (Delft University of Technology, The Netherlands)Bruin Benthem (Dutch Space B.V., The Netherlands)

13:00 Lunch in the ESTEC Restaurant

14:00 Exchange of Thermal Models — Challenges and SolutionsStefan Kasper (Jena-Optronik GmbH, Germany)

14:25 The KT Thermal Mapping Tool — an semi-automated temperature transfer betweenstructural and thermal models

Anton Zhukov & Markus Czupalla & Alexander Kuisl & Gerhard Bleicher & Winfried Gambietz(Kayser-Threde GmbH, Müchen, Germany)

14:50 Mapping nodal properties between dissimilar nodal representations of S/C structuresusing ESATAN-TMS

Alexander Maas (Dutch Space, The Netherlands)

15:15 MASCOT — Thermal subsystem designLuca Celotti & Riccardo Nadalini & Małgorzata Sołyga (ActiveSpace Technologies GmbH, Germany)

Volodymyr Baturkin (DLR Institut für Raumfahrsysteme, Germany)Sergey Khairnasov & Vladimir Kravets (National Technical University of Ukraine, Ukraine)



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16:00 LHP MODULE SOFTWARE — Application at System LevelPaul Atinsounon & David Valentini (Thales Alenia Space, France)

16:25 Time dependent behaviour of pumped two-phase cooling systems — Experiments andSimulations

Henk Jan van Gerner (NLR, The Netherlands)

16:50 Study on the utilization of the FHTS extension of ESATAN-TMS for the thermalmodeling of a bi-propellant satellite propulsion system

Martin Schröder (OHB System AG, Germany)

17:15 Thermal Modeling of CubeSats and Small SatellitesAnwar Ali & M. Rizwan Mughal & Haider Ali & Leonardo M. Reyneri

(Department of Electronics and Telecommunications, Politecnico di Torino, Italy)

17:40 Social Gathering in the Foyer

19:30 Dinner in La Toscana


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Programme Day 2

9:00 E-THERM POLICYThierry Basset & Patrick Hugonnot (Thales Alenia Space, France)

9:25 ESATAN Thermal Modelling Suite — Product Developments and DemonstrationChris Kirtley & Henri Brouquet (ITP Engines UK Ltd, United Kingdom)

movies/media6

10:10 SYSTEMA-THERMICA — Launcher Case Set-up and Thermal AnalysisTimothée Soriano & Rose Nerriere (Astrium SAS, Toulouse, France)


11:20 First Application of Esatan-TMS r6 Solids for a Launcher Upper Stage ThermalModel

Harold Rathjen (Atrium, Bremen, Germany)

11:45 Enhancement of ray tracing method for radiative heat transfer with new Isocellquasi-Monte Carlo technique and application to EUI space instrument baffle

Lionel Jacques (Centre Spatial de Liège, Belgium)Luc Masset & Gaetan Kerschen (University of Liège, Space Structures and Systems Laboratory, Belgium)

12:10 Calculation of Optimal Solar Array Steering Laws for Temperature Critical MissionsAndreas Brandl (Astrium GmbH Ottobrunn, Germany)

Jan-Hendrik Webert (Universität der Bundeswehr Müchen, Germany)

12:35 BepiColombo MTM STM Thermal TestScott Morgan (Astrium EADS, United Kingdom)

13:00 Closure

13:00 Lunch in the ESTEC Restaurant


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Appendix A

Welcome and introduction

Harrie Rooijackers(ESA/ESTEC, The Netherlands)


10 Welcome and introduction


17

Appendix B

Thermal Concept Design ToolFlux calculation results and the new tool presentation

Andrea Tosetto Matteo Gorlani(Blue Engineering, Torino, Italy)

Harrie Rooijackers(ESA/ESTEC, The Netherlands)


18 Thermal Concept Design Tool — Flux calculation results and the new tool presentation

Abstract

During its lifetime the TCDT has evolved both through improvements suggested or required by usersall over the ESA member states and enhancements as part of the development and maintenance contractwith ESA.The current release 1.6.0 of the TCDT is already available to the European Thermal Community andcontains an internal flux calculator for TCDT models. This flux calculator has been validated throughcomparison of results with ESATAN-TMS r5.The evolution of the tool that is now under development will be a portable stand-alone application,independent of Excel, that can be more easily integrated in existing workflows. Skilled engineers will beable to easily extend the tool with their only script, re-using the existing functionality, in order to performtheir analysis in an easier way. To maximise the functionality available in the basic tool, participants areinvite to discuss their ideas and suggestions with us directly during the breaks or contact us after theworkshop.


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Appendix C

Evaluation of Heat Transfer Parameters from CFD for Use inTMM in Case of Gas Convection in Vented Cavities

Christian Wendt(Astrium Space Transportation, Bremen, Germany)


34Evaluation of Heat Transfer Parameters from CFD for Use in TMM in Case of Gas Convection

in Vented Cavities

Abstract

The analysis of the convection in Ariane 5 launcher’s vented cavities on ground and during ascent isimportant for the thermal control of the equipments and of the propellants during flight phase. For theaccording analysis of the upper stage, a lumped parameter Thermal Mathematical Model (TMM) hasbeen established within ESATAN.As an input, heat transfer parameters (HTPs) have been derived from two related Computational FluidDynamic (CFD) analysis cases, the so called hot and cold case. The methodology for evaluation of theseHTPs from the CFD analysis is described for one and more gas nodes based on steady state results. For arepresentative launcher cavity with laminar/turbulent buoyancy influenced flow, a comparison is providedbetween the TMM results and the CFD results obtained with the commercial tool ANSYS Fluent. Exactagreement is achieved between TMM and CFD for the hot and the cold case. Deviations for the analyzedintermediate cases turned out to be less than 5K in case of a one gas node TMM and less than 3K in caseof a seven gas node TMM.


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Appendix D

Introduction to Simulation Data Management

Peter Bartholomew(MDAO Technologies, United Kingdom)


44 Introduction to Simulation Data Management

Abstract

This presentation will give an introduction to the topic of Simulation Data Management. This is currentlya hot topic in industrial areas such as automotive or aeronautics, however, for the space thermal analysiscommunity it is still quite new. The objective of the presentation is to give an overview of the field and tostimulate discussion about how space thermal analysis models could be managed and how the analysistools could be developed to facilitate this.


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Appendix E

EVATHERM for Early Validation of Thermal Control

Fabrice Mena(Astrium SAS, France)


60 EVATHERM for Early Validation of Thermal Control

Abstract

Commercial telecommunication programs require a more and more demanding reduced schedule for theintegration & validation phases of the satellites.The validation of the Thermal Control System (TCS) which is mission dependant represents a majoractivity which drives the schedule competitiveness. This aspect becomes a key challenge especially whenthe satellite is a prototype such as Alphabus PFM platform or Neosat, with new features and enhancedarchitectures, implying higher technical risks to be removed at the earliest in the program.The analysis of a typical satellite Assembly, Integration & Test sequence gives the evidence thatconsidering the extensive system testing in clean room at ambient pressure & temperature, there is anopportunity to perform an early validation and correlation of the satellite Thermal Mathematical Model(TMM) prior to the Thermal Vacuum & Thermal Balance testing.Thus, the presentation will give an overview of the Evatherm method for Early Validation of the ThermalControl, developed together with ESA in the frame of Artes 3-4 and implemented in a real industrial andchallenging Satcom program as Alphasat.This engineering approach and associated software tools allow first to perform temperatures predictionsand model correlation of the satellite system through testing in clean room, all along the AIT sequence,and second to implement Real time, Innovative & Improved Analysis methods (IAMITT) during thesatellite Thermal Vacuum test itself.The benefit in terms of thermal architecture performances justification or workmanship verification hasbeen substantial and the methodology and the tools are now intended to be used as a standard.


73

Appendix F

Thermo-electrical Detailed Analysis

François Mercier B. Samaniego V. Gineste L. Gajewski A. du Jeu(Astrium SAS, Toulouse, France)


74 Thermo-electrical Detailed Analysis

Abstract

An important part of the power system engineering work is deeply linked to the thermal aspects of thevarious power components like batteries and solar panels. With the help of an internally developedcoupled thermo-electrical solver, previously untried detailed analyses on various power systems wereperformed in Astrium, stemming interesting results.The wide-spread Thermisol thermal solver in the Systema software suite was extended with a power add-on. The principle was to add an electrical layer through dedicated nodes complementary to the existingthermal nodes. It allowed the power users to code electrical systems and user components on the sameenvironment as the existing Thermisol codes.This new solver was applied for a full satellite power system analysis. The coupling with the thermalaspect allowed the re-use of thermal files and designs to prepare the analysis. An electrical layercomposed of the user components of a classical power system (battery, solar array, power regulationand distribution) was added to perform fully coupled thermo-electrical analysis, adding higher accuracyto the battery, solar array and regulation modeling.In the frame of an ESA study to investigate on solar array thermal / electrical imbalance in power systemsequipped with MPPT, in-depth modeling of solar panels were also performed on both electrical andthermal aspects. This allowed cell level analysis for very fine phenomenon like the local cell gradientscreated by dissipation of back panel diodes and harness during orbit cycles, sensitivity studies to defaultor accurate local and global shadowing analyses.The solver was also included in a software loop with coupled SAS/MPPT hardware for validation testing.


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Appendix G

Correlating thermal balance test results with a thermalmathematical model using evolutionary algorithms

Niek van Zijl B. Zandbergen(Delft University of Technology, The Netherlands)

Bruin Benthem(Dutch Space B.V., The Netherlands)


90Correlating thermal balance test results with a thermal mathematical model using evolutionary

algorithms

Abstract

The results of a series of thermal balance tests have been correlated with a thermal mathematical model.Three different optimization algorithms have been used for this: Monte Carlo simulation, GeneticAlgorithm and Adaptive Particle Swarm Optimization. Based on a correlation criterion that minimizesthe temperature difference between tests and model, the correlation can be optimized. APSO proved tobe most useful, for its ability to optimize both locally and globally, its ability to search in a continuoussearch space, and its fast convergence. In this research, an average residual error of only 1.1◦C was found.In general, optimization algorithms are feasible for thermal balance test results correlation. Comparing tomanual correlation, optimization algorithms take less time, yield better results since they scan the entiresearch space, and are more flexible since several uncertain parameters can be varied at the same time.However, optimization techniques tend to find mathematical solutions rather than physical solutions, soboundaries on the parameter space are needed, for example from other tests. Even though this researchindicates a good correlation, the set-up was relatively small (only 129 nodes and 24 relevant temperaturemeasurements and comparisons) and comprehensible. For larger (satellite) test programs, the thermalnetwork might be less easily understood and contain more unknowns and uncertainties. In that case acorrelation using optimization techniques might be less optimal. Some engineering judgement of thethermal engineer will always be needed.

Note: An article explaining the method in more detail is included behind the presentation.


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Appendix H

Exchange of Thermal ModelsChallenges and Solutions

Stefan Kasper(Jena-Optronik GmbH, Germany)


110 Exchange of Thermal Models — Challenges and Solutions

Abstract

This presentation deals with the various challenges of exchanging thermal models that can be encoun-tered by:

• use of different thermal software tools

• use of different ESATAN-TMS versions

• use of different modeling rules / model design standards

• differences in thermal modeling specification documents


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Appendix I

The KT Thermal Mapping Toolan semi-automated temperature transfer between structural and thermal models

Anton Zhukov Markus Czupalla Alexander Kuisl Gerhard BleicherWinfried Gambietz

(Kayser-Threde GmbH, Müchen, Germany)


120The KT Thermal Mapping Tool — an semi-automated temperature transfer between structural

and thermal models

Abstract

The analysis of the thermo-opto-mechanical performance of optical instruments is a complex and timeconsuming process. It spans across multiple disciplines and multiple tools (e.g. ESATAN, NASTRAN,ZEMAX) which are not designed to interface with one another.To allow precise end-to-end thermo-opto-mechanical analyses of instruments, without the loss of data,KT establishes a software suite (MULTIPAS), which inherently connects the thermal, structural andoptical tools.An important part of the MULTIPAS software suit is the Thermal Mapping Tool (TMT) providing thelink between the thermal and structural model. The tool realize an automated temperature mappingprocess based on in-house interpolations routines and has the ability to handle mismatching meshes ofthe thermal and structural models.To preserve thermal boundaries between the parts a recognition of single parts is built in the TMT,allowing to map geometrically adjacent but thermally decoupled parts correctly. Further, edge effectsare covered in a way that guarantees no extrapolations at the edges, preserving the temperature rangeprescribed by the thermal model. A built in batch mode allows for handling of thousands of time steps,opening the door to transient stability analyses of entire orbits.Demonstration of the TMT functionality, results from application experience will be presented anddiscussed in the presentation. Further, conclusions shall be presented and discussed for the build ofGMMs which are to be used as mapping "templates".


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Appendix J

Mapping nodal properties between dissimilar nodalrepresentations of S/C structures using ESATAN-TMS

Alexander Maas(Dutch Space, The Netherlands)


138Mapping nodal properties between dissimilar nodal representations of S/C structures using

ESATAN-TMS

Abstract

When multiple parties are involved in a single project, they often use different (thermal) models torepresent a particular part or structure. As the nodal distribution is not always the same, it can bedifficult to exchange data (e.g. flux distributions and temperature profiles) from one party to another.Clever use of a standard ESATAN-TMS tool can simplify the mapping of nodal data from one nodalrepresentation to another for some of these applications, i.e. where the geometric models are sufficientlysimilar such that the conductive interfaces between the different node systems can be calculated byESATAN-TMS. By using the conductive area calculation tool, the contact area between the differentnodal representations can be determined. By means of area averaging, any nodal parameter can beprojected onto the other nodal representation system. This process requires a few manual steps that canbe performed automatically by means of a script. The method has been successfully applied in a detailedS/A plume flux analysis, where plume flux distributions determined in one nodal system were appliedto a more detailed model to determine the S/A temperatures. This application is used as an example toshow all required steps.


151

Appendix K

MASCOTThermal subsystem design

Luca Celotti Riccardo Nadalini Małgorzata Sołyga(ActiveSpace Technologies GmbH, Germany)

Volodymyr Baturkin(DLR Institut für Raumfahrsysteme, Germany)

Sergey Khairnasov Vladimir Kravets(National Technical University of Ukraine, Ukraine)


152 MASCOT — Thermal subsystem design

Abstract

MASCOT is a lander built by DLR, embarked on JAXA’s Hayabusa-2, a scientific mission to study theasteroid 162173 1999 JU3. It is a small lander, less than 300x300x200mm?, with onboard payloads(camera, magnetometer, radiometer and IR spectrometer), developed in collaboration by DLR andCNES. MASCOT lands on the asteroid surface, after being released by Hayabusa-2 from a very closeposition above the asteroid surface, and investigates the asteroid surface. The thermal design of the landerrepresents one of the main challenges in the whole project because of multiple constraints, depending onthe mission phase, mass, power and free space available.MASCOT, notwithstanding its small size, is equipped with redundant heat-pipe system, MLI blanket,heaters. The thermal design of the lander has been chosen after a trade-off phase concerning thetechnology which could suit better the opposing requirements of the mission: low heat exchange betweenthe lander and the exterior (including the main spacecraft) in cruise, possibility to transfer all the heatdissipated by the internal paylaods and electronic boards during operations on asteroid surface. Afterselecting the heat-pipe technology as baseline, a development phase was undertaken by the partners bothin terms of manufacturing, testing, thermal characterization phase and analitical modelling in order tomatch the thermal requirements.Heaters are used to assure the survival of the most delicated parts of the lander during cold cruise phases:the battery cells (only primary battery on-board), the electronic boards and the main payload. Strictrequirements are given by the main spacecraft in terms of maximum power available to heat the landerduring cruise. MLI blankets are used where the available space allows it, e.g. to extra insulate the Eboxfrom the rest of the lander creating a „hot compartment" and between the lander and the main spacecraftto reduce the heat exchange with it during cruise below the given limits. The whole thermal concept inall its parts undertook a detailed modelling phase in parallel to an experimental phase in vacuum chamberto improve the model and to qualify the system.MASCOT thermal design is here presented through the following points:

• MASCOT as part of HY-2 mission: mission, constraints, challenges

• Challenging thermal requirements

• Main thermal strategy and trade-offs: available technologies, constant conductance heat-pipes

• Thermal design

• Vacuum chamber testing

• Thermal model results

• Conclusions and future steps


165

Appendix L

LHP MODULE SOFTWAREApplication at System Level

Paul Atinsounon David Valentini(Thales Alenia Space, France)


166 LHP MODULE SOFTWARE — Application at System Level

Abstract

Loop Heat Pipes (LHPs) are more and more used for spacecraft thermal control thanks to itsperformances and ability to transport heat load on a long distance.In the frame of CSO program, LHPs are implemented on Visible and Infra-Red Detection Sub-assemblies.In order to simulate LHPs behaviour at system level, specific software was developed by Astrium /Thales Alenia Space under CNES and ESA fundings. The LHP Module is compatible with many thermalsoftwares and works as a sub-model of ESATAN-TMS Thermal Mathematical Model (TMM).The objectives of the presentation are to describe briefly the LHP Module inputs/outputs and functionalblocks. Main performances of Visible and Infra-Red Assemblies are simulated using the LHP Module.Breadboard test exploitations are compared with predictions in order to validate the LHP Moduleaccuracy. The software limits and constraints will also be presented.


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Appendix M

Time dependent behaviour of pumped two-phase cooling systemsExperiments and Simulations

Henk Jan van Gerner(NLR, The Netherlands)


178Time dependent behaviour of pumped two-phase cooling systems — Experiments and

Simulations

Abstract

Two-phase pumped cooling systems (see figure M.1) are applied when it is required to maintain a verystable temperature in a system, for example in the AMS02, which was launched with the space shuttle(in May 2011) and subsequently mounted on the International Space. However, a two-phase pumpedcooling system can show complex dynamic behaviour in response to rapid heat load variations. Forexample, when the heat load is increased, a large volume of vapour is suddenly created, which results ina liquid flow into the accumulator and an increase in the pressure drop. This will result in variations inthe pressure and therefore temperature in the system, which are undesired. It is difficult to predict andunderstand this behaviour without an accurate dynamic model. For this reason, such a model has beendeveloped by NLR. The model numerically solves the one-dimensional time-dependent compressibleNavier-Stokes equations, and includes the thermal masses of all the components (see figure M.2 for anexample). The model has been used for different projects, and the numerical results show an excellentagreement with experiments. During the presentation, I will discuss different pumped two-phase coolingsystems, and a comparison between simulations and experiments.

Figure M.1: Schematic drawing of a two-phasepumped cooling system Figure M.2: Calculated vapour mass fraction


193

Appendix N

Study on the utilization of the FHTS extension of ESATAN-TMSfor the thermal modeling of a bi-propellant satellite propulsion

system

Martin Schröder(OHB System AG, Germany)


194Study on the utilization of the FHTS extension of ESATAN-TMS for the thermal modeling of a

bi-propellant satellite propulsion system

Abstract

The presentation will contain the findings of my diploma thesis done in cooperation with OHB SystemAG. Its aim was to investigate if the FHTS extension of ESATAN-TMS could be used to model the fluidinside a bi-propellant chemical propulsion system with regard to the thermal control system. At first, aFHTS fluid library for propellants and pressurizing agents was implemented in order to model the fluidsin the propulsion system accurately. After that, two simplified thermal models using the fluid librarywere developed, one for the pressure control assembly (PCA) and another for the propellant insulationassembly (PIA). For both models inputs from a reference geostationary telecommunication satellite wereused. The presentation will mainly deal with the modeling of the effect of gas cooling by the expansion ofHelium gas through the gas pressure regulator of the PCA. The solution found will be explained and theresults of the simulations shown. Eventually several best practices and lessons learnt shall be presentedwith regard to the use of FHTS for propulsion systems.


205

Appendix O

Thermal Modeling of CubeSats and Small Satellites

Anwar Ali M. Rizwan Mughal Haider Ali Leonardo M. Reyneri(Department of Electronics and Telecommunications, Politecnico di Torino, Italy)


206 Thermal Modeling of CubeSats and Small Satellites

Abstract

Recently universities and SMEs (Small and Medium Enterprises) have initiated the development ofnanosatellites because of their low cost, small size and short development time. The challenging aspectsfor these satellites are their small surface area for heat dissipation due to their limited size. There isnot enough space for mounting radiators for heat dissipation. As a result thermal modeling becomes avery important element in designing a small satellite. A generic thermal model of a CubeSat satellite ispresented in this paper. Detailed and simplified thermal models for nanosatellites have been discussed.The detailed model takes into account all the thermal resistors associated with the respective layer whilein the simplified model the layers with similar materials have been combined together and representedby a single thermal resistor. The thermal model of complete CubeSat has been presented. The proposedmodels have been applied to CubeSat standard nanosatellite called AraMiS-C1, developed at Politecnicodi Torino. Thermal resistances measured through both models are compared and the results are in closeagreement. The absorbed power and the corresponding temperature differences between different pointsof the single panel and complete satellite are measured. In order to verify the theoretical results, thethermal resistance of the AraMiS-C1 is measured through an experimental setup. Both values are inclose agreement.Detailed thermal model of the CubeSat panel from top to bottom is shown in figure O.1 and will befurther explained in the presentation. Simplified thermal model of the CubeSat panel from top to bottomis shown in figure O.2 and will be further explained in the presentation.

Figure O.1: CubeSat panel cross sectional viewand detailed thermal model

Figure O.2: Panel top to bottom cross sectionalview and simplified model

Thermal model of the complete CubeSat is shown in figure O.3 and will be further explained in thepresentation.

Figure O.3: CubeSat satellite and top to bottom thermal model


221

Appendix P

E-THERM POLICY

Thierry Basset Patrick Hugonnot(Thales Alenia Space, France)


222 E-THERM POLICY

Abstract

In Thales Alenia Space - Cannes, we have a long experience and expertise, in thermal softwaredevelopment. Concerning this point, we work with external companies in particular with DOREA.The subject concerns the presentation, the demonstration of a new thermal software in TAS-Cannes(= e-Therm release 1.4.c), and the associated policy. This tool is funded entirely by TAS-Cannes and itshould not have to be commercialised but freely distributed.Then, we will to talk about industrialization strategy especially based on using of our thermal softwareand on the integration of expert tools: Pre-processing, Orbitography module, 2D-3D Conductive module,Radiative module, Solver module, Thermal model reduction tool, PTA (which is a tool dedicated topreliminary phases and very well adapted to the telecom program), Post-processing. The general aimof these evolutions is to improve and standardize the analysis process, in order to gain in cost, qualityand input/output traceability. This calculation chain is entirely compatible with thermal analysis COTS,main CAD and mechanical tools, thanks to powerful interfaces. These modules have been successfullyused on following programs : Apstar, Yamal, W6A, O3B, Iridium Next, 8WB, TKM, CSO ...Moreover, to improve quality and reliability of the dynamic spacecraft simulator and for performancereasons, TAS-Cannes chooses e-Therm to be the thermal real-time simulator engine based on thethermal mathematical model (TMM) provided by thermal analysis team. External powers calculatorand temperatures resolution from internal e-Therm core module have been successfully improved to fitthe real-time constraints. Parallelisation has been largely used to make the calculation most reactive inorder to fit as much as possible the physics behaviour. New SCSIM based on TMM has been successfullyvalidated on Alphasat (@bus platform) and O3B Networks satellite.On another hand and to answer customer’s needs, TAS-Cannes needed to provide a real time payloadconfiguration simulator. A new session has been implemented into e-Therm. This session providesfor each daily configuration a detailed thermal cartography for each channels based on powerful post-processing outputs (Barchart, CAD view ...). This session will be used on 8WB program planned to runall over the satellite lifetime.In parallel of industrialization strategy, we develop a strategy of openness of e-Therm by distributingsoftware free of charge to TAS-Toulouse for antenna applications, TAS-Turin for infrastructures andinstruments and more generally to TAS-Group and to others companies.Furthermore, e-Therm can be used for concurrent design facility applications, and to other fields inphysics: electronic board thermal behaviour calculation, ESD simulation on geostationary satellite.


235

Appendix Q

ESATAN Thermal Modelling SuiteProduct Developments and Demonstration

Chris Kirtley Henri Brouquet(ITP Engines UK Ltd, United Kingdom)


236 ESATAN Thermal Modelling Suite — Product Developments and Demonstration

Abstract

ESATAN-TMS provides a complete and powerful integrated thermal modelling environment. ESATAN-TMS r6 sees a major evolution of the product, with advances to its geometry modelling and 3Dvisualisation capabilities. This presentation outlines the developments going into the new release ofthe product.A demonstration of ESATAN-TMS r6 will be given, building a model to demonstrate the newfunctionality.


261

Appendix R

SYSTEMA-THERMICALauncher Case Set-up and Thermal Analysis

Timothée Soriano Rose Nerriere(Astrium SAS, Toulouse, France)


262 SYSTEMA-THERMICA — Launcher Case Set-up and Thermal Analysis

Abstract

Thermal analyses of launchers have specific constraints which have been integrated in the up-comingrelease 4.7 of SYSTEMA-THERMICA. This presentation illustrates through a demonstration the newlyintegrated features allowing a launcher case set-up.A new catalogue of volume primitives, required for modeling the launcher, has been added. The softwarehandles the generation of external coating and internal bulk nodes and also automatically switches theactivities according to contact detections.On the mission aspects, launcher trajectories and attitudes are usually defined by discretized dataexpressed in complex inertial frames (synchronization of rotational frames related to the launcher baseposition).Once the geometrical model and mission are set-up, the thermal analysis can start.The thermal analysis of the previously defined launcher case requires the computation of the conductioninto the volume structures as well as radiative exchanges between external coatings, planet Albedo andIR, solar and aero-thermal fluxes.The presentation focuses on the volume management and on the new aero-thermal flux module whichintegrates an atmospheric model.Besides, the new SYSTEMA version 4.7 has new post-processing features: from the generation ofmission log data to the comparison of different thermal cases and margins set-up, results based on thelauncher case are exploited.


279

Appendix S

First Application of Esatan-TMS r6 Solids for a Launcher UpperStage Thermal Model

Harold Rathjen(Atrium, Bremen, Germany)


280 First Application of Esatan-TMS r6 Solids for a Launcher Upper Stage Thermal Model

Abstract

The development of this new feature of Esatan was driven by the need for thermal software that allowsa volumetric modeling for heavy launcher structures and the applied thermal protection with thicknessesof up to several cm. This presentation assesses the first experiences with this tool applied on an existingupper stage model created within the Ariane 6 development program. Due to the early project statuswith a limited number of nodes this model is considered a good test. The advantages in particular of theautomatic conductor generation (ACG) in comparison with the previous shell approach will be discussed.


291

Appendix T

Enhancement of ray tracing method for radiative heat transferwith new Isocell quasi-Monte Carlo technique and application to

EUI space instrument baffle

Lionel Jacques(Centre Spatial de Liège, Belgium)

Luc Masset Gaetan Kerschen(University of Liège, Space Structures and Systems Laboratory, Belgium)


292Enhancement of ray tracing method for radiative heat transfer with new Isocell quasi-Monte

Carlo technique and application to EUI space instrument baffle

Abstract

The finite element method (FEM) is widely used in mechanical engineering, especially for spacestructure design. However, FEM is not yet often used for thermal engineering of space structures wherethe lumped parameter method is still dominant. Radiative exchange factors (REFs), used to calculateradiative thermal exchanges in space, are usually computed through Monte Carlo ray-tracing. Due to thelarge number of elements composing a FE model, the computation of the REFs is prohibitively expensive.In the frame of a global approach, several research axes will be investigated to reduce the computationaleffort of the REFs with FEM. The first one focuses on accelerating the convergence and enhancing theaccuracy of the ray-tracing process to decrease the number of rays required to achieve a given accuracy.The developments of the new Isocell quasi-Monte Carlo ray tracing method are presented. Based onNusselt’s analogy, the ray direction sampling is carried out by sampling the unit disc to derive the raydirections. The unit disc is divided into cells into which random points are then generated. The cellshave the particularity of presenting almost the same area and shape. This enhances the uniformity of thegenerated quasi-random sequence of ray directions and leads to faster convergence. This Isocell methodhas been associated with different surface sampling to derive the REFs. The method is benchmarkedagainst ESARAD, the standard thermal analysis software used in the European aerospace industry.Various geometries have been used. In particular, one entrance baffle of the Extreme Ultraviolet Imager(EUI) instrument developed at the Centre Spatial de Liège in Belgium is used. The EUI instrument of theSolar Orbiter European Space Agency mission and will be launched in a Sun-centered (0.28 perihelion)orbit in 2018.


303

Appendix U

Calculation of Optimal Solar Array Steering Laws forTemperature Critical Missions

Andreas Brandl(Astrium GmbH Ottobrunn, Germany)

Jan-Hendrik Webert(Universität der Bundeswehr Müchen, Germany)


304 Calculation of Optimal Solar Array Steering Laws for Temperature Critical Missions

Abstract

For the Solar Orbiter and Bepi Colombo missions it is required to steer the solar arrays of the Spacecraftsin such a way that sensitive parts (like solar cells) do not exceed a maximum temperature, while keepingthe electric power output as high as possible. This is usually done by adapting the sun aspect angle ofthe array in dependency of the actual heat input from the sun and if present from the planet.In this presentation a fast and accurate method is discussed in which the optimized solar array rotationangles at each orbit position are calculated by a modified iteration-scheme with a detailed solar arraythermal model.With the developed iteration scheme it became possible to limit the total number of time consumingcalculations of the time dependent radiation exchange factors to a minimum without losing the stability ofthe scheme. A further decrease of computational time was achieved by splitting the radiation calculationinto sub-processes. Those have been distributed among the available computers, leading to an efficientparallelization of the radiation calculations.


311

Appendix V

BepiColombo MTM STM Thermal Test

Scott Morgan(Astrium EADS, United Kingdom)


312 BepiColombo MTM STM Thermal Test

Abstract

BepiColombo is a joint ESA/JAXA mission to Mercury, and will provide the best understanding ofthe planet to date. Mercury’s proximity to the sun has called for significant thermal design work onthe spacecraft, with many new technologies being developed specifically for the project. This in turnhas demanded a large amount of spacecraft testing and validation. This presentation will describe theMercury Transfer Module (MTM) system level STM thermal test, detail the specific challenges faced,and report the results and the lessons learned from the correlation of the associated thermal model.


321

Appendix W

List of Participants

Ali, AnwarPolitecnicoPolitecnico di Torino - Corso Duca degli Abruzzi10147 TorinoITALYk [email protected]

Atinsounon, PaulTHALES ALENIA SPACE100, boulevard du Midi06156 Cannes La BoccaFRANCEk [email protected]

Bakker, MarijeNational Aerospace Laboratory NLRVoorsterweg 318316PR MarknesseNETHERLANDSk [email protected]

Bartholomew, PeterMDAO TechnologiesUnited Kingdomk [email protected]

Bascheri, OlivierDOREALes Alisiers Bat B1 Route des Alisiers ZI des 3Mo06600 ANTIBESFRANCEk [email protected]

Basset, ThierryTAS-Cannesbd du midi06150 Cannes la BoccaFRANCEk [email protected]

Baturkin, VolodymyrDLR, Institute of Space SystemsRobert-Hooke-Str. 728359 BremenGERMANYk [email protected]

Beaumont, HelenITP Engines UK LtdCambridge Road, WhetstoneLE8 6LH LeicesterUNITED KINGDOMk [email protected]


322

Benthem, RoelandNational Aerospace Institute NLRAntony Fokkerwegweg 21059 CM AmsterdamNETHERLANDSk [email protected]

Bodendieck, FrankOHB System AGUniversitaetsallee 27-2928359 BremenGERMANYk [email protected]

Brandl, AndreasASTRIUM GmbHRobert-Koch-Str. 182024 TaufkirchenGERMANYk [email protected]

Brouquet, HenriITP Engines UK LtdCambridge Road, WhetstoneLE8 6LH LeicesterUNITED KINGDOMk [email protected]

Brunetti, FrançoisDOREALes Alisiers Bat B1 Route des Alisiers ZI des 3Mo06600 ANTIBESFRANCEk [email protected]

Capitaine, AndréASTRIUM3 rue des CosmonautesToulouseFRANCEk [email protected]

Celotti, LucaActive Space TechnologiesGERMANYk [email protected]

Checa, ElenaESTEC/ESAKeplerlaan 12200 AG NoordwijkNETHERLANDSk [email protected]

Czupalla, MarkusKayser-Threde GmbhGERMANYk [email protected]

De Palo, SavinoThalesAlenia SpaceStrada Antica di Collegno, 25310146 TorinoITALYk [email protected]


323

Etchells, JamesESA/ESTECKeplerlaan 12201 AZ NoordwijkNETHERLANDSk [email protected]

Fagot, AlainDOREALes Alisiers Bat B1 Route des Alisiers ZI des 3Mo06600 ANTIBESFRANCEk [email protected]

Fernandez Rico, GermanUniversidad Politécnica de Madridplaza del cardenal cisneros, 328040 MadridSPAINk [email protected]

Ferreira, PedroMax Planck Institute for Solar System Research(MPMax-Planck-Str. 237191 Katlenburg-LindauGERMANYk [email protected]

Fishwick, NickAstrium Ltd.Gunnels Wood RoadSG1 2AS StevenageUNITED KINGDOMk [email protected]

Franzoso, AlbertoCGS SpAVia Gallarate 15020151 MilanoITALYk [email protected]

Friso, EnricoIndependent Consulting EngineerVia A.Pizzamano, 40/A35127 PADOVAITALYk [email protected]

Gibson, DuncanESA/ESTECKeplerlaan 12201 AZ NoordwijkNETHERLANDSk [email protected]

Gorlani, MatteoBlue Engineeringvia Albenga 9810098 Cascine Vica, RivoliITALYk [email protected]

Hulier, Jean-PierreASTRIUM51-61 route de verneuil78130 les mureauxFRANCEk [email protected]


324

Iugovich, StéphaneASTRIUMFRANCEk [email protected]

Jacques, LionelUniversity of LiegesBELGIUMk [email protected]

Jahn, GerdAstrium GmbHClaude-Dornier-Strasse88090 ImmenstaadGERMANYk [email protected]

Jarrier, AntoineDOREALes Alisiers Bat B1 Route des Alisiers ZI des 3Mo06600 ANTIBESFRANCEk [email protected]

Karaismail, F. N.Turkish Aerospace Industries, Inc.Fethiye Mah. Havacilik Blvd. No:17 Akýncý06980 AnkaraTURKEYk [email protected]

Kasper, StefanJena-Optronik GmbHPruessingstrasse 4107745 JenaGERMANYk [email protected]

Kirtley, ChrisITP Engines UK LtdCambridge Road, WhetstoneLE8 6LH LeicesterUNITED KINGDOMk [email protected]

Laine, BenoitESA/ESTECKeplerlaan 12201 AZ NoordwijkNETHERLANDSk [email protected]

Lardet, PaulSodernAvenue Descartes94451 Limeil-Brévannes CedexFRANCEk [email protected]

Laskowski, JessicaDLR (Cologne)Linder Höhe51147 CologneGERMANYk [email protected]


325

Lein, SebastianJena-Optronik GmbHPrüssingstraße 4107745 JenaGERMANYk [email protected]

Leroy, SandrineDOREALes Alisiers Bat B1 Route des Alisiers ZI des 3Mo06600 ANTIBESFRANCEk [email protected]

Lindenmaier, PeterHPS GmbHHofmannstr. 25-2781379 MünchenGERMANYk [email protected]

Maas, AlexanderDutch SpaceMendelweg 302333CS LeidenNETHERLANDSk [email protected]

Mena, FabriceEADS AstriumFRANCEk [email protected]

Mercier, FrançoisEADS ASTRIUM SAS31 rue des cosmonautes31402 ToulouseFRANCEk [email protected]

Molina, MarcoSelex ESviale Europa20014 NERVIANOITALYk [email protected]

Moroni, DavidAVIOC.SO GARIBALDI, 2200034 COLLEFERROITALYk [email protected]

Münstermann, RolfAstrium GmBHAirbus-Allee 128199 BremenGERMANYk [email protected]

Nadalini, RiccardoActive Space TechnologiesITALYk [email protected]


326

Nerriere, RoseEADS ASTIUM31 avenue des Cosmonautes31402 ToulouseFRANCEk [email protected]

Okan, AltugTUBITAK UZAYODTU Kampusu, Inonu Blv.06531 AnkaraTURKEYk [email protected]

Pasquier, Marie-HélèneCNES18 AVENUE EDOUARD BELIN31401 TOULOUSEFRANCEk [email protected]

Pin, OlivierESAKeplerlaan 22200AG NoordwijkNETHERLANDSk [email protected]

Price, StevenAstriumGunnels Wood RoadSG1 2AS StevenageUNITED KINGDOMk [email protected]

Rathjen, HaroldAstrium GmbH Space TransportationAirbus-Allee 128199 BremenGERMANYk [email protected]

Romera Perez, Jose AntonioESA/ESTECKeplerlaan, 12200 AG NoordwijkNETHERLANDSk [email protected]

Rooijackers, HarrieESA/ESTECKeplerlaan 12201 AZ NoordwijkNETHERLANDSk [email protected]

Santoni, MassimoSelex ESVia A. Einstein50013 Campi BisenzioITALYk [email protected]

Schröder, MartinOHB System AGUniversitätsallee 27-2928359 BremenGERMANYk [email protected]


327

Schwaller, DavidESA-ESTECKeplerlaan 12201 AZ NoordwijkNETHERLANDSk [email protected]

Scott, MorganAstrium UKGunnels Wood RoadSG1 2AS StevenageUNITED KINGDOMk [email protected]

Selin, A.TAI-TURKISH AEROSPACE INDUSTRIESFethiye Mahallesi, Havacilik Bulvari No:17Kazan-06980 ANKARATURKEYk [email protected]

Shaenko, A.Dauria Aerospacest. Novaya, 100, Business center "Ural", Moscowre143025 Technopark "Skolkovo"RUSSIAN FEDERATIONk [email protected]

Soriano, TimothéeAstrium SAS3 rue des cosmonautes31402 ToulouseFRANCEk [email protected]

Stroom, CharlesMYOBGerrit van der Veenstraat 169-hs1077EB AmsterdamNETHERLANDSk [email protected]

Supper, WolfgangESA/ESTECKeplerlaan 12201 AZ NoordwijkNETHERLANDSk [email protected]

Theroude, ChristopheAstrium Satellites31 rue des cosmonautes31402 ToulouseFRANCEk [email protected]

Tosetto, AndreaBlue Engineeringvia Albenga 9810098 Cascine Vica, RivoliITALYk [email protected]

Turkmenoglu, MustafaTUBITAK SPACE TECHNOLOGIESRESEARCH INSTITUTEODTU KAMPUSU TUBITAK UZAY06531 ANKARATURKEYk [email protected]


328

Uygur, A. B.Turkish Aerospace Industries, Inc.Fethiye Mah. Havacýlýk Bul. No 1706980 AnkaraTURKEYk [email protected]

Valentini, DavidTHALES ALENIA SPACE100 boulevard du Midi06156 Cannes la BoccaFRANCEk [email protected]

van Gerner, Henk JanNLRVoorsterweg 318316PR MarknesseNETHERLANDSk [email protected]

Wendt, ChristianAstrium Space Transportation GmbHAirbus Allee 128361 BremenGERMANYk [email protected]

Zamboni, AndreaSELEX ESViale Europa SNC20014 NervianoITALYk [email protected]

Zevenbergen, PaulDutch SpaceMendelweg 302333CS LeidenNETHERLANDSk [email protected]


27th european space thermal analysis workshop · between the tmm results and the cfd results...

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